A Thickness Optimization Design Method of Turbine Blade Thermal Barrier Coating

A technology for turbine blade and thickness optimization, applied in the field of surface coating protection, can solve the problems of inability to optimize the thickness distribution design, lack of evaluation of the pros and cons of TBCs thickness design, achieve simple and efficient TBCs thickness optimization design, reduce the amount of analysis and calculation, Effects of low stress levels

Active Publication Date: 2019-11-08
XI AN JIAOTONG UNIV
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Problems solved by technology

However, the current existing technology can only qualitatively give the rough distribution of the thickness of TBCs of turbine blades, and cannot realize the accurate optimal design of thickness distribution, and lacks the evaluation of the advantages and disadvantages of TBCs thickness design

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  • A Thickness Optimization Design Method of Turbine Blade Thermal Barrier Coating
  • A Thickness Optimization Design Method of Turbine Blade Thermal Barrier Coating
  • A Thickness Optimization Design Method of Turbine Blade Thermal Barrier Coating

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Embodiment Construction

[0048] The present invention will be further described in detail below in conjunction with specific embodiments, which are to explain rather than limit the present invention.

[0049] The optimized design process of the present invention is as follows figure 1 As shown, in order to better understand the technical solution of the present invention, the above optimization design method is applied to the TBCs thickness design of gas turbine turbine blades. figure 2 shown.

[0050] The specific process of this embodiment includes the following steps:

[0051] Step 1: Determine the thickness of each layer of TBCs.

[0052] The TBCs comprise a ceramic layer, an adhesive layer and a thermally grown oxide layer. The thickness of the selected ceramic layer is k×100 μm, where k is the number of the analysis times, that is, the repetition times of step 1 to step 6, k=1, 2, . . . , 10. The thickness of the adhesive layer selected in this embodiment is 150 μm, and the thickness of the...

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Abstract

The invention discloses a thickness optimization design method for thermal barrier coatings (TBCs) of a turbine blade, and belongs to the technical field of surface coating protection. Representative nodes uniformly distributed on the turbine blade are selected, the states of local regions are reflected by temperatures and stress results of representative node positions, and TBCs thickness analysis of a complex blade is equivalent to thickness optimization design of a finite number of representative node positions, so that the analysis calculation amount is reduced; a mathematic formula is established for reflecting design objectives of high heat insulation performance, low stress level and low preparation cost, calculation is performed by introducing a multi-objective optimization algorithm to obtain optimal ceramic layer thickness of each representative node position, and a total objective function value is taken as a TBCs thickness optimization design and evaluation parameter of the blade, so that the advantages and disadvantages of a TBCs thickness distribution scheme can be quantitatively evaluated and the shortcoming that an existing method only can perform qualitative evaluation is overcome; and the method can ensure the service safety of the coatings and improve the usage efficiency of the coatings.

Description

technical field [0001] The invention belongs to the technical field of surface coating protection, in particular to a method for optimizing the thickness of a thermal barrier coating of a turbine blade. Background technique [0002] Thermal barrier coatings (TBCs) are advanced ceramic-metal multilayer material systems that are widely used in modern turbine engines. By coating the surface of high temperature hot end parts such as engine combustion chamber and turbine blades with TBCs with low thermal conductivity, on the one hand, the surface temperature of metal parts can be reduced or the gas inlet temperature of engine turbine blades can be further increased, and on the other hand, metal parts can be protected from Corrosion and oxidation of high temperature gas, so as to achieve the purpose of prolonging the service life of hot end components and improving engine efficiency. Taking a gas turbine blade as an example, the combined effect of TBCs and internal cooling of the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/17G06F30/23G06F2111/04G06F2111/06
Inventor 李彪王铁军范学领李定骏江鹏
Owner XI AN JIAOTONG UNIV
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